CN109070552A - Mixed component with internal cooling channel - Google Patents

Mixed component with internal cooling channel Download PDF

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Publication number
CN109070552A
CN109070552A CN201680084607.XA CN201680084607A CN109070552A CN 109070552 A CN109070552 A CN 109070552A CN 201680084607 A CN201680084607 A CN 201680084607A CN 109070552 A CN109070552 A CN 109070552A
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CN
China
Prior art keywords
laminate
cooling duct
component
cooling
stack
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201680084607.XA
Other languages
Chinese (zh)
Inventor
拉梅什·苏布拉马尼亚
沃尔特·H·马鲁西克
罗伯特·J·麦克莱兰
德里克·布拉德丘利斯
斯特凡·兰彭舍夫
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of CN109070552A publication Critical patent/CN109070552A/en
Pending legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/40—Structures for supporting workpieces or articles during manufacture and removed afterwards
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F12/00—Apparatus or devices specially adapted for additive manufacturing; Auxiliary means for additive manufacturing; Combinations of additive manufacturing apparatus or devices with other processing apparatus or devices
    • B22F12/40—Radiation means
    • B22F12/41—Radiation means characterised by the type, e.g. laser or electron beam
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/34—Laser welding for purposes other than joining
    • B23K26/342—Build-up welding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
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    • C04B37/02—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles
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    • F01D5/14—Form or construction
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    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24273—Structurally defined web or sheet [e.g., overall dimension, etc.] including aperture
    • Y10T428/24322—Composite web or sheet
    • Y10T428/24331—Composite web or sheet including nonapertured component
    • Y10T428/24339—Keyed
    • Y10T428/24347—From both sides

Abstract

Provide a kind of component (30), the component (30) is stacked in another one by multiple laminates (10,32) one and is formed, to limit the stack laminate structure (25) with leading edge (18) and rear (20).Each laminate in the multiple laminate (10,32) is formed by ceramic-base complex material (11).In addition, it is defined multiple internal cooling channels (22) in the inside (21) of stack laminate structure (25), and the multiple internal cooling channel (22) is longitudinally extended between leading edge (18) and rear (20).Metal support structure part (36) is arranged to extend through the first opening (28) in laminate and extends through stack laminate structure.

Description

Mixed component with internal cooling channel
Technical field
The present invention relates to high-temperature component and it is related to being used to form the process of high-temperature component.More specifically, of the invention is each Aspect is related to mixing (ceramic-base complex (CMC) and the gold of one or more internal cooling channels for having formed therein Belong to) component.
Background technique
Gas turbine includes shell or cylinder, for accommodating compressor section, combustor section and turbine portion.Supply Air is compressed in compressor section and is guided in combustor section.Compressed air enters entry of combustion chamber simultaneously And it is mixed with fuel.Then, air/fuel mixture burn is to generate the gas of high temperature and pressure.Then, which advances Pass through combustion chamber transition part and enters in the turbine portion of turbine.
In general, turbine portion includes rows of guide vane, working gas is directed to turbo blade by the guide vane Airfoil portion.Working gas is advanced through turbine portion, and then rotates turbo blade, so that rotor be made to rotate.Rotor It is also attached to compressor section, to make compressor rotate and also rotate generator to generate electricity.The high efficiency of gas turbine It is to be realized by the way that the gas for flowing through combustor section is heated to feasible high temperature.However, hot gas is flowing The various metal worm components deterioration that when crossing turbine hot gas may pass through, the metal worm component is such as burning Room, transition conduit, guide vane, ring portion section and turbo blade.
For this purpose, having been developed that the strategy for protecting turbine part from extreme temperature, for example research and development and selection are suitable for bearing The high-temperature material of these extreme temperatures, and to the cooling strategy that holding member during operation is fully cooled.The prior art High temperature alloy with additional protective coating layer is commonly used in the hot gas path component of gas turbine.However, it is contemplated that in high temperature Substantive and long-term development in terms of the field of alloy, it is extremely difficult for further increasing the heat resistance of high temperature alloy.
It is up to 1200 DEG C in addition, having had developed temperature tolerance and there is higher potential resistance to height in local non-critical areas Ceramic-base complex (CMC) material of warm nature.Further, despite the presence of challenge, such as the environmental protection in different engineerings, But other CMC materials with more high temperature tolerance are had developed.Under any circumstance, CMC material may include ceramics or Ceramic based material, any one of ceramics or ceramic based material have multiple reinforcing fibers.In general, fiber can have it is scheduled Orientation, to provide additional mechanical strength for CMC material.It has been found, however, that due to also difficult other than other factors Fiber is oriented with the edge in many turbine parts of typical complicated shape in component, therefore by CMC material Forming turbine part, there may be challenges.Component is formed by by stack CMC laminate for this purpose, having had developed.Stack CMC laminate includes by having the CMC material of the fiber in expected orientation to be formed by multiple laminates.By including respectively having There are multiple flat laminates of desired fiber orientation and shape, overall constitute of component can pass through increased option with shape It is better controlled.However, although oxide CMC material and non-oxidized substance CMC material can be subjected to high temperature, due to outer Portion surface is exposed to the substantially also gas path burning gases of heat, therefore oxide CMC material and non-oxidized substance CMC than 1200 DEG C Material can only be subjected to high temperature in the case where not carrying out cooling in burning situation and continue the limited period.Therefore, right In fully or substantially needing further exist for improved cooling strategy by the component that CMC material is formed.
Summary of the invention
Inventors have developed for providing in closed in mixing (CMC/ metal) stack laminate structure The system and process of portion cooling duct, which includes that one is stacked in another one Multiple laminates.As will be elucidated below, mixed structure includes the multiple CMC laminates stacked around metal support structure part And the embedded internal cooling channel in portion of CMC.On the one hand, embedded internal cooling channel solve for for mixing Component provides additional and substantially cooling needs.In addition, embedded internal cooling channel has reduced or eliminated the gold of mixed component Leakage at category-ceramic interface.If in the selected stack laminate only in stack laminate cutting channel and High pressure cooling fluid (it has pressure more higher than the pressure of the exterior section of component) is flowed into cooling duct, then this to let out Leakage will occur.
According to one aspect, a kind of gas turbine component is provided, which includes:
Multiple laminating sheets, the multiple laminate one are stacked in another one to limit stack laminate structure, should Stack laminate structure has leading edge and rear, and each laminate in the multiple laminate includes ceramic-base complex material Material；
Multiple internal cooling channels, the multiple internal cooling channel are limited at the inside of stack laminate structure Interior, each cooling duct in the cooling duct is longitudinally extended between the leading edge and rear of stack laminate structure； And
Metal support structure part, the metal support structure part are arranged to extend through the first opening in laminate and prolong Extend through stack laminate structure.
A kind of process for being used to form component is provided according to another aspect, which includes:
It is defined in multiple by multiple first laminates and the second laminate around metal support structure part is formed therein The stack laminate structure of portion cooling duct, the first laminate and the second laminate respectively include ceramic-base complex material, First laminate respectively further includes the cooling duct in its at least one side, and the cooling duct is in the first laminate Leading edge and rear between be longitudinally extended.
Detailed description of the invention
The present invention is illustrated with reference to the accompanying drawings in the following description, attached drawing is shown:
Fig. 1 is the perspective view of component according to another aspect of the present invention, and the component is by multiple first laminates and second Laminate is formed and the component wherein has embedded cooling duct；
Fig. 2 is the sectional view of the component of Fig. 1, which wherein has embedded internal cooling channel；
Fig. 3 is the perspective view of exemplary layer one pressing plate according to an aspect of the present invention, the exemplary layer one pressing plate With cooling duct formed therein；
Fig. 4 is the perspective view of exemplary second laminate according to an aspect of the present invention；
Fig. 5 illustrates the cross section of cooling duct according to an aspect of the present invention；
Fig. 6 illustrates the cross section of the cooling duct with side wall according to an aspect of the present invention, wherein the side wall With rough surface；
Fig. 7 to Fig. 8 illustrates the laminate wherein with align structures according to an aspect of the present invention；
Fig. 9 illustrates preforming metal support structure part according to an aspect of the present invention；
Figure 10 illustrates according to an aspect of the present invention inclined between metal support structure part and CMC material ontology Set component；
Figure 11 to Figure 17, which is respectively illustrated, according to an aspect of the present invention has embedded cooling duct for manufacture The step of during mixing CMC/ metal parts；
Figure 18 illustrates the stack laminate structure including CMC laminate according to an aspect of the present invention, the CMC The part of laminate and metal support structure part is overlapping.
Specific embodiment
Referring now to attached drawing, Fig. 1 illustrates mixing (CMC/ metal) components 30 formed by multiple laminates 10,32, should Mixing (CMC/ metal) component 30 is, for example, gas turbine blades 44, as described in this article, the multiple laminate 10,32 1 Person is stacked in one to generate stack laminate structure 25.On the one hand, component 30 includes the first of suitable number and combination Laminate 10 and the second laminate 32, as will be referring to Fig. 3 is illustrated to Fig. 4.In addition, as shown, metal support structure Part 38 extends radially through CMC laminate 10,32, to provide additional mechanical support for laminate 10,32.Fig. 2 is Fig. 1 The sectional view of (at the line II-II of Fig. 1 intercept), and Fig. 2 illustrate it is multiple embedded in stack laminate structure 25 Cooling duct 22.Except the use of CMC material and stack laminate, cooling duct 22 is that stack laminate structure 25 mentions For adding cooling strategy.
Fig. 3 illustrates exemplary layer one pressing plate 10 according to an aspect of the present invention, the exemplary layer one pressing plate 10 Including ceramic-base complex (CMC) material 11, ceramic-base complex (CMC) material 11 can be used to form according to the present invention The mixed component of one side.In the embodiment as shown, the first laminate 10 includes having top surface 14 and bottom surface 16 ontology 12, top surface 14 and bottom surface 16 extend between leading edge 18 and rear 20.In addition, the first laminate 10 wraps Cooling duct 22 is included, which is limited at top surface 14 and the bottom in the first laminate 10 and being located at ontology 12 One or both of surface 16 is upper or interior.Each cooling duct 22 in the interior section 21 of ontology 12 and can be laminated It is longitudinally extended between the leading edge 18 and rear 20 of plate.The embodiment illustrated shows following cooling ducts 22: the cooling Channel 22 has uniform distance between cooling duct 22 and the outer surface or outer peripheral edge of the first laminate 10；It should be understood, however, that , the invention is not limited thereto.In other embodiments, the outer surface or outer peripheral edge of cooling duct 22 and the first laminate 10 The distance between can be changed according to the cooling requirement at the associated position of laminate 10.
As being shown in FIG. 3, in some embodiments, ontology 12 may include entrance 24 and outlet 26, the entrance 24 for cooling fluid to be introduced into cooling duct 22, and the outlet 26 is for being discharged cooling fluid from channel 22.In reality It applies in mode, entrance 24 can be arranged at the leading edge 18 of the first laminate 10 or be arranged to the leading edge with the first laminate 10 18 is adjacent, and export 26 can be arranged at the rear 20 of the first laminate 10 or be arranged to after the first laminate 10 Edge 20 is adjacent.Entrance 24 is at least in fluid communication with the fluid such as air conveyed from suitable fluid source.In addition, the first laminate 10 further include one or more openings 28, and metal support structure part 38 can pass through the opening 28 and be formed or with its other party Formula arrangement finally mixes (CMC/ metal) component 30 and provides mechanical support to be used for, as will be elucidated below.
First laminate 10 is characterized in that the first laminate 10 includes at least one cooling duct 22, and the cooling is logical Road 22 is formed in (longest dimension of ontology) top surface 14 or bottom surface 16, and described in some embodiments Cooling duct 22 is formed in 16 the two of surface 14 and surface.In addition, component 30 may include any number formed therein Internal cooling channel 22.Similarly, it although the first laminate 10, which is shown as, has single continuous coo1ing channel 22, answers Understand, the invention is not limited thereto and each first laminate 10 may include on selected side or surface 14,16 Two or more cooling ducts spaced apart 22.In addition, being followed although each channel 22 is shown as having herein Predictable parabola/straight line path of the outer surface profile of corresponding laminate, it should be understood that the present invention is not limited to This.Channel 22 can limit any suitable access for cooling fluid.In embodiments, special modality 22 can be such as Limit the serpentine path of disengaging plane.
Fig. 4 illustrates exemplary second laminate 32 according to an aspect of the present invention, exemplary second laminate 32 It also include that there is top surface 14 and the ontology of bottom surface 16 12, top surface 14 and bottom surface 16 are in leading edge 18 and rear Extend between 20.In some embodiments, the second laminate 32 further includes entrance 24, which is placed in the first laminate 10 Entrance 24 above, allow cooling fluid to flow radially through component 30 when being provided to component 30.With this side Formula, the entrance 24 of each laminate 10,32 in stack will be collectively form collection chamber (plenum) 29 (Fig. 1), cooling Each cooling that fluid can be flowed in the collection chamber 29 to be transported to cooling fluid in the cooling duct 22 in component 30 Channel.
In some embodiments, the second laminate 32 can be identical with the first laminate.In other embodiments In, the second laminate 32 can be characterized in that, the second laminate 32 is at least one following side or surface: described at least one A side or surface do not have cooling duct 22 formed therein.In some embodiments, without cooling duct 22 Side can be stacked on the first laminate 10 and be used for fenced cooling duct 22.However, the invention is not limited thereto.? In some embodiments, the first laminate 10 and the second laminate 32 can be stacked in one with one, so that the first laminate 10 cooling duct 22 and the cooling duct 22 of the second laminate are overlapped to be formed to have and represent the first laminate 10 and the second layer The cooling duct 22 of the depth of 32 combination depth of pressing plate.
In some embodiments, two surfaces 14,16 of the second laminate 32 do not include wherein cooling duct 32, are such as existed Shown in Fig. 4.In another embodiment, at least one of top surface 14 and bottom surface 16 do not include cooling logical Road.On the other hand, the second laminate 32 can have perpendicular to its longest dimension and smaller than the height of the first laminate 10 high Degree.Under any circumstance, when the second laminate 32 is disposed on the first laminate 10 or is linked with the first laminate 10 Second laminate 32 can provide suitable structure and be embedded in heap to fenced corresponding cooling duct 22 and by cooling duct 22 In the inside of stacked laminate structure 25, as shown in Figure 2.
It should be understood that individual first laminate 10 for being used to form required component 30 can be with other the first laminations Plate 10 is roughly the same.This is also same for the second laminate 32.However, in some embodiments, at least one first Laminate 10 can be different from another first laminate 10, and at least one second laminate 32 can be with another second lamination Plate 32 is different.For example, this dissimilarity may include thickness, size, shape, density, fiber orientation, cooling duct size, hole The difference of porosity etc..In some embodiments, any one of laminate 10,32 or more laminate can be in plate Form, can have straight or curved edge and can have such as airfoil shape.In other embodiments, Selected pairs of laminate 10,32 can have the abutment surface of non-flat forms.In addition, the first laminate 10 and the second laminate 32 can be it is identical or different from each other (for example, in the side such as thickness, size, shape, density, fiber orientation, porosity Face).
Each cooling duct 22 can have any suitable size (example for being suitable for the cooling of degree needed for component provides Such as, depth and width).Only by way of example, each cooling duct 22 may include from about 0.25mm to about 5mm Depth and from about 0.25mm to the width of about 5mm.As used in this article, refer to can be in elaboration value for term " about " ± 10% in the range of value.In addition, each cooling duct 22 can have the cross section of any desired shape, such as polygon Shape shape.In embodiments, as shown in 5, polygonal shape may include the cross section of trapezoidal shape 34.More In specific embodiment, trapezoidal shape 34 wherein may include round base portion part 36, as shown.In other embodiments In, cooling duct cross-sectional shape can be rectangular or curved (for example, semicircle or half elliptic).In addition, cooling logical The surface in road 22 can have different degrees of roughness or finish.In some embodiments, one in cooling duct 22 A or more cooling duct may include fin, pillar, button or the similarity piece to increase the heat transfer mechanisms in channel 22.
In addition, each cooling duct 22 can use any suitable equipment or process well known in the prior art, such as It is formed in the ontology 12 of the first laminate 10 or the second laminate 32 via process equipment or suitable Laser Power Supply.At certain In a little embodiments, when using laser source to provide cooling duct 22, laser source can be for example including YAG laser or titanium dioxide Carbon laser source.In operation, energy can be by from laser source towards the selected top of the ontology 12 of corresponding laminate 10,32 Surface 14 or bottom surface 16 guide, so that CMC material 11 is heated to following temperature in regional area: the temperature is enough to make Depth needed for material vaporization and removal is to form each cooling duct 22.It should be understood that more than one spacer portion (channel) It may be necessary and for forming the channel 22 of intended shape and size for providing any other in cooling duct 22 Desired character --- further groove in the such as side wall in restriction channel 22 --- is necessary.
On the other hand, cooling duct 22 further includes any suitable additional cooling Enhanced feature.Only by way of example, The interior surface 35 in channel 22 can also include rough surface 37 as shown in fig. 6.Rough surface 37 can be provided and is used for Enhancing is cooling or enhancing is transmitted with the hot of cooling fluid for flowing through channel 22.Rough surface 37 can pass through during forming Laser or milling provide.Alternatively, rough surface 37 can be by buckling as known in the art for channel 22 is additional It is provided with (trip strip).In another embodiment, rough surface 37 can pass through blasting treatment or any other conjunction Suitable process or equipment provides.In other embodiment, in any one side wall 40 or two for defining cooling duct 22 It can be set on a side wall 40 and be parallel to the extension or recessed to extend with cooling duct 22 at non-parallel angle of cooling duct 22 Slot.
On the other hand, the first laminate 10 and/or the second laminate 32 can have align structures, which helps In the positioning of the first laminate 10 and the second laminate 32 on each other.Any suitable structure can be used for the purpose.Reference Fig. 7 shows exemplary layer one pressing plate 10 according to an aspect of the present invention, which includes cooling Channel 22 and there is recess portion 31, recess portion 31 be sized to receive extend from the ontology 12 of exemplary second laminate 32 it is corresponding Protruding portion 33.In some embodiments, opposite arrangement can be provided.As being shown in FIG. 8, as any embodiment party Formula is the same, the first laminate 10 and the second laminate 32 can be stacked on one in another one and through heat-treated (fire or Sintering), so that cooling duct 22 is embedded in laminate and the first laminate 10 is linked to the second laminate 32 with shape At laminate group 66, which wherein has embedded cooling duct 22.
As set forth above, each of the first laminate 10 and the second laminate 32 can be completely or partially It is formed by CMC material 11.CMC material 11 may include ceramics or ceramic based material, each of ceramics or ceramic based material With multiple reinforcing fibers.In some embodiments, CMC material 11 can at least have with regard to CMC material 11 in different directions It can be for the meaning for having varying strength characteristic anisotropic.It should be understood that including material selection and fiber orientation Various factors may influence the strength characteristics of CMC material.In addition, CMC material 11 may include oxidisability CMC material and non-oxygen The property changed CMC material.In embodiments, CMC material 11 includes oxide CMC material as known in the art.
In some embodiments, CMC material 14 may include ceramic matrix (aluminium oxide), and fiber is (for example, 3M is public The 720 high temperature oxidation resisting fiber of Nextel of department) it may include the aluminium silicon salt sour component being made of aluminium oxide and silica.It is fine Dimension can provide in a variety of manners, such as woven fabric, blanket, unidirectional tape and cushion.For manufacturing CMC material Various technologies are well known in the art and these technologies can be used to be formed for using CMC material herein 11.In addition, in United States Patent (USP) No.8,058,191, No.7,745,022, No.7,153,096, No.7,093,359 and No.6 describes exemplary CMC material 11 in 733,907, the full content of each application in these applications by reference simultaneously Enter herein.As mentioned, the selection of material may not be the single factor for determining the characteristic of CMC material 11, because of fiber side To the mechanical strength that may also for example influence material.The fiber of CMC material 11 can have any suitable orientation as a result, than As described in United States Patent (USP) No.7,153,096.
As mentioned, individual laminate 10,32 described above can be used to form component 30.In a reality It applies in mode, being formed by component 30 by a pile laminate 10,32 as described in this article may include for gas turbine Fixation member, such as fixed guide vane, which may include lower part shown in upper brace portion and Fig. 1 Platform part 42.In another embodiment, component 30 may include rotary part for gas turbines, the such as (figure of blade 44 1).However, the invention is not limited thereto and can form any desired component according to process described herein.
In addition, component 30 will include metal support structure part 38 when being formed, which radially prolongs The corresponding opening 28 in laminate 10,32 is extended through, such as in Fig. 1 to shown in Figure 2.Each metal support structure part 38 A degree of mechanical support is provided for component.Although CMC material provides fabulous thermal protection performance, CMC material Mechanical strength is less than the mechanical strength of corresponding high-temperature alloy material resistant to high temperature still significantly.For this purpose, metal support structure Part 38 is the material that CMC material supplement has bigger mechanical strength.In some embodiments, laminate 10,32 can be with such as It is successively arranged on provided metal support structure part 34 with ring is arranged in the mode on bar, can such as be seen referring to Fig. 9 It arrives.Then, have the laminate 10,32 for being formed with internal cooling channel 22 can be via to the heap laminate 10,32 Compressed and keep laminate be in compressive state holding structure or other structures and be kept/compress.
Metal support structure part 38 can be attached to one with by individual laminate or lamination board group according to another aspect, Heap CMC laminate 10,32 and via increasing material manufacturing process in such a way that one layer connects one layer pass through heap CMC laminate 10,32 in Corresponding opening 28 constructed." Hybrid Ceramic Matrix Composite Materials is (mixed entitled Close ceramic matric composite) " PCT application No.PCT/US2015/023017 in elaborate to form this metal support knot The exemplary increasing material manufacturing process of component 38, all the contents of the application are incorporated herein by reference.It will also be below to being used for The example process that each metal support structure 38 is formed via increasing material manufacturing is described.
Metal support structure part 38 is formed with extra play pressing plate provides several advantages.Only by way of example, The metal support structure part 38 manufactured in a manner of increasing material can permit to be in for each laminate height in stack Metal is with the interface of optimization of the offer compared with known method between CMC material, or is allowed for the difference in the same part CMC/ metal configuration.The advantage may be particularly critical in the forming of bigger component such as gas turbine component, this be because It is bigger for component, it is expected that the difficulty at optimization interface is provided between CMC material and metal along the entire radical length of component 30 It is bigger.Therefore, in some embodiments, metal support structure part 38 can with a laminate 10,32 associated parts And have relative to metal support structure part and another different laminate 10,32 associated parts different components, Shape and size.
In some embodiments, metal support structure part 38 may be configured so that allow will be from the sheet of laminate 10 The load transfer of body 12 is to metal support structure part 38.In order to facilitate this, in some embodiments, metal support structure part 38 can be deviated by following suitable structures and one or more laminates in laminate 10,32: the structure is protected It holds the supporting force between metal support structure part 38 and ontology 12 including CMC material 22 and is also allowed in metal support knot Load transfer is carried out between component 38 and ontology 12.It also elaborates to realize this in PCT application No.PCT/US2015/023017 The suitable structure of kind effect.By way of example, as being shown in FIG. 10, biasing member 46 is provided, wherein in gold There are gap 48, the biasing members 46 between category supporting structure 38 and the ontology 12 of corresponding laminate (for example, laminate) To adapt to the load transfer between metal support structure part 38 and corresponding laminate such as laminate 10.In addition, biasing structure The presence of part 46 can permit for the different thermal expansions between metal support structure part 38 and corresponding laminate 10,32. Without limitation, biasing member 46 may include multiple leaf springs as shown 50 or including have to a certain degree Elasticity any other type structure or material.
In another embodiment, biasing member 46 can be for example including additional metal part, and the additional metal part is logical Increasing material manufacturing process is crossed to be formed to have a greater degree of biasing/bullet provided for the part relative to metal support structure part 38 The lattice or other structures of property.In yet another embodiment, biasing member 46 may include multiple relative stiffnesses fingers (by Metal or the like formation), it is inclined that one of the fingers keep metal support structure part 38 corresponding in laminate 10,32 It moves.In yet another embodiment, any metal support structure part in metal support structure part 38 wherein can also include cooling Channel, for example, along the metal support structure part longest size extend through supporting structure inside cooling duct, Wherein, cooling duct is at least with suitable fluid fluid communication for passing through cooling duct for fluid such as air delivery.
Metal support structure part 38 may include following any suitable metal materials: the metal material will be laminate And/or component provides additional strength, and the metal material will be allowed for by contacting with CMC material 11 or by close Make CMC material 11 that metal support structure part 38 be diverted heat to carry out to a certain degree CMC material 11 close to CMC material 11 Cooling.In some embodiments, metal material may include high temperature metallic material as known in the art, such as Ni-based High-temperature alloy material or cobalt base superalloy material.Term " high temperature alloy " is construed as referring to even if at high temperature still Show the resistance to high corrosion of fabulous mechanical strength and tolerance creep and the alloy of resistance to oxidation.Exemplary high temperature alloy material is city Sell obtainable and entitled Hastelloy, Inconel alloy of trademarks and brands (for example, IN 738, IN 792, IN 939), Rene alloy (for example, Rene N5,41 Rene, Rene 80, Rene 108, Rene 142, Rene 220), Haynes alloy, Mar M, 247 CM, CM 247LC, C263,718, X-750, ECY 768,262, X45, PWA1483 and CMSX (for example, CMSX-4) single crystal alloy, GTD 111, GTD 222, MGA1400, MGA2400, PSM 116, CMSX-8, CMSX-10, PWA 1484, IN 713C, Mar-M-200, PWA1480, IN 100, IN 700, Udimet 600, Udimet 500 and titanium aluminide.
The process described herein for manufacturing component described herein is proposed according to another aspect,. The example process for being used to form component according to an aspect of the present invention will be described by being described below.In an embodiment party In formula, which can manufacture gas turbine component as known in the art, which can be rotary part Or fixation member, such as blade or guide vane.Referring now to fig. 11 to Figure 18, stationary guide blades pass through the process illustrated Formed, it is to be understood that the present invention be not generally limited to process described herein or to stationary guide blades or The manufacture of gas turbine component.Alternatively, component may include any other suitable object.
Firstly, as shown in fig. 11, the generally flat plate 52 including CMC material 11 can be provided.It can be from plate 52 are cut into the ontology 12 of any one or more laminate 10,32 as described in this article, have desired to be formed The laminate of shape (for example, airfoil shape), wherein there is desired feature in the desired body shape.One side It cooling duct 22 as described in this article, entrance 24, outlet 26 and opens for example, when to provide the first laminate 10 in face One of mouth 28 or more persons can be formed in ontology 12 or be formed through ontology 12, or be formed in top surface 14, it in bottom surface 16, or is formed in 16 the two of top surface 14 and bottom surface.The formation of laminate and its feature can To be completed by machining, water jet cutting, and/or laser cutting or any other suitable method.In certain embodiment party In formula, cooling duct 22, entrance 24, outlet 26 and opening one of 28 or more persons can also with the first laminate 10 Identical mode be formed through ontology or be formed in the top surface 14 and/or bottom surface 16 of the second laminate 32 On.However, in some embodiments, being not provided with cooling duct 22 in the second laminate 32, and therefore, the second laminate 32 by with do not have cooling duct 22 the first laminate 10 in a manner of identical mode formed.Form expectation laminate 10,32 The process steps can repeat, until formed needed for number each type of laminate 10,32 until.Of course, it is possible to from Buy prefabricated laminate 10,32 in suitable source.
Several advantages can be provided by forming laminate 10,32 by plate 52.For an advantage, plate provides heavily fortified point Solid reliable and statistically consistent form CMC material 11.Therefore, flatbed manner can be to avoid in manufacture tight bend configuration When the manufacture that has already appeared it is difficult.For example, plate can be unfettered during curing, and therefore plate not by each to different The contraction strain of property.In addition, reducing the criticality of laminated devices defect using plate, which is difficult to.In addition, It is formed accurately and is processed as certain shapes since plate can use cost-effective cutting method, is easier to realize ruler Very little control.Slab construction also makes it possible expansible and automation manufacturing process.It is formed by the process steps Laminate structure part 10,32 be shown in Fig. 3 as discussed previously into Fig. 4.
Alternatively, laminate 10,32 can be initially initially formed instead of having desired shape in substantially flat type The generally flat skeleton mode of shape provides, and keeps firm reliable and statistically consistent form CMC material 11 simultaneously. Flat skeleton technology includes drawn fibers material or the commercially fibrous material of drawing, such as Nextel 610,720 With 650.According to specific application and required component, the fiber of drawing can have the expection thickness, big of one or more determinations Small, shape, density, fiber orientation, fiber architecture etc..Next, the fiber of elongated drawing with such as by twisted, rolling, Any mode in the various modes of tack welding, injection molding, spraying and similar fashion etc works, to be configured to the phase Hope the generally flat skeleton of shape.After flat skeleton is shaped, ceramic base oxidation material can be deposited in fiber skeleton And be deposited on around fiber skeleton, to be mutually connected by formula either in following various ways with fiber skeleton It connects, the mode is such as molded, sprays, splash, fusing, infiltration, molten slurry infiltration etc., wherein ceramic base oxidation material is such as Commercially available ceramic base oxidation material such as Pritzkow FW12 (its matrix be alumina zirconia mixture) or For ceramic base oxidation material described in United States Patent (USP) No.7,153,096, No.7,093,359 and No.6,733,907.Root According to specific application and required component, in case of need, the generated laminate 10,32 including CMC material 11 can have There are the expection thickness of one or more determinations, size, shape, density, porosity, pore character etc..In PCT application The process for executing the embodiment is elaborated in No.PCT/US2015/060053, the full content of the application passes through ginseng Draw and is incorporated herein.
In addition, generally flat skeleton described above can modify, to form thicker shape, rather than substantially Flat shape.If modified in this way, three-dimensional framework shape can generally be led with required component, such as gas turbine 3D shape to blade or blade is consistent.This modification includes being stacked to drawn fibers or using thicker drawing fibre Dimension, to be configured to thicker skeleton.
Referring now to fig. 12, base component 54 can be provided, multiple first laminates 10 are stacked on the base component 54 With the second laminate 32.In some embodiments, laminate 10,32 is individually disposed on base component, is stacked with constructing Formula laminate structure.As mentioned, embedded cooling duct 22 will be formed in stack in stack laminate structure 25 At the selected part of laminate structure.This can be by stacking the first laminate 10 and the second laminate 32 so that the first lamination Plate 10 and the second laminate 32 are limited to one or more closed cooling ducts 22 in laminate 10,32 to realize.With Afterwards, in some embodiments, the two laminates can be sintered/be melted through Overheating Treatment, such as sintering process by laminate It is combined together.In this way, a possibility that having reduced or eliminated the cooling fluid loss between adjacent laminate.At it In his embodiment, two or more laminates 10,32 for forming corresponding internal cooling channel 22 can be sintered in list In only position (far from stacking), to be fused together laminate as the laminate with two or more laminates Group 66, then which can be arranged on laminate.Sintering can be carried out and be continued with any suitable temperature Duration appropriate, and in one embodiment, sintering can be with to be linked to two adjacent laminates each other About 500 DEG C to 1000 DEG C of 1 hour to 24 hours time of constant temperature carries out.
In this embodiment, base component 54 may include the platform for stationary guide blades or blade, such as diameter To inside platform.Alternatively, base component 44 can be any other suitable structural member, for example is wherein not formed and appoints Second laminate 32 of what opening.In other embodiments, base component 54 can also be for example including one layer of metal material, should Layer metal material can be arranged on platform.Under any circumstance, selected laminate 10,32 or lamination board group 66 are with its expectation Order is disposed on base component 54.
In some embodiments, (or the metal support structure of one or more metal support structure parts 38 is provided The part of part 38), each metal support structure part in one or more metal support structure part 38 is from base component 54 radially, as being shown in FIG. 8.In embodiments, laminate 10,32 or laminate are to as needed sequentially It is stacked on metal support structure part 38, until the formation of complete stack laminate structure 25.Therefore, in the embodiment party In formula, metal support structure part 38 can be prefabricated and scale cun, to adapt to laminate 10,32 in the metal support structure part 38 On arrangement.
According to another aspect, metal support structure part 38 on the contrary with laminate 10,32 or lamination board group 66 stack and It is constructed in situ via increasing material manufacturing, to form complete stack laminate structure 25.Referring for example to Figure 12, Metal Source materials 58 are affixed to the required position in the opening 28 of one or more laminates 10,32.In embodiments, from suitable gold Category source 56 such as hopper or similarity piece provide metal material 58 in powdered form with predetermined volume and feed speed.
After metal material 58 deposits, the such as laser source of energy source 60 is melted according to for being formed in corresponding opening 28 The predetermined scheme of metal and a certain amount of energy 62 is focused on the metal material 58 in corresponding opening 28, with fusing in pre- The metal material 58 of the predetermined amount of random sample formula.In order to realize this as a result, energy source 60 can be mobile relative to main body laminate, Or main body laminate can be mobile relative to energy source 60, and energy source 60 is located in the required position on main body laminate Place, and then melt metal material 48.Molten metal will be allowed either actively or passively to cool down, to provide two sections of gold spaced apart Belong to supporting structure 38.Therefore, these parts can limit the section 64 of corresponding metal support structure part 38, the section 64 In each section can extend through the corresponding opening in each laminate in the laminate 10,32 of stack 28。
In this embodiment, in order to construct metal support structure part 38 and in order to facilitate the part subsequently formed On the top of the additional section 64 being previously formed of 64A, additional metal material 58A can be attached on the top of section 64, As in figure 13 illustrates.Then, energy source 60 (Figure 12) can guide a certain amount of energy 62 to melt additional metal again Material 64A, and generated melted material can be allowed to cooling (either actively or passively) and such as be shown in Figure 14 with being formed The section 64 subsequently formed out, each section in the section 64 can be laminated at that time from the top in stack The top surface of plate (proud) vertically-arranged tallly.
In embodiments, the metal core 64A subsequently formed can be now used as pillar, subsequent laminate 10, 32 or lamination board group 66 (as shown) can be arranged into above section 64 on the pillar, as being shown in FIG. 15.The mistake Journey can repeat again and again, until being entirely laminated the formation of plate stack 25, as being shown in FIG. 16.This design One the advantage is that metal support structure part 38 various pieces can for corresponding laminate 10,32 or group 66 especially The various pieces of customization or metal support structure part 38 can be in any desired way (for example, about load or heat transmitting Size, shape, material, and/or between CMC material and metal support structure part have required interface) be customized.
Only by way of example, in the case where the stack of 20 laminates, if preforming length and it is rigid Property rod piece from lamination plate stack radially outer end to lamination plate stack radial inner end extend through lamination sheetpile Overlapping piece will then be difficult between CMC material and metal support structure part 38 have preferable interface along entire radical length.Change sentence It talks about, the structure formed is bigger, then will more be difficult to provide expectation at each radial position of the component formed Specification, such as the optimization interface between CMC material and metal.Therefore, by being constructed through layer by layer using increasing material manufacturing Size/parameter, CMC material and the gold of the metal support structure part 38 of stack laminate structure 25, CMC material and/or metal Any other structural member in interface and component between category can be optimized along the radical length of component with various intervals. This customization is for example impossible in the case where long pole or similarity piece.
According to another aspect, under applicable circumstances, during the formation of metal support structure part 38, gap 48, biasing Component 46 or any other desired character described herein can also be incorporated in opening 28 during increasing material manufacturing process Or it is otherwise formed in opening 28.It will also be appreciated that the formation in gap 48 can be by using removable interval Part and/or by being controlled to spacing etc. of the increasing material manufacturing parameter such as between laser intensity, duration, energy source and component It makes and carries out.
As being shown in FIG. 16, when last laminate 10,32 or group 66 are affixed to stack, it is formed with The formation of the lamination plate stack 25 of multiple cooling ducts 22 is completed.Then, if necessary or in case of need, Ke Yiti The top surface of component 30 is limited for overhead 68, the top surface of component 30 can limit in this case is such as scheming Stationary guide blades 70 shown in 17.In shown embodiment, overhead 68 can be in stationary guide blades It include outer radial platform in situation.In other embodiments, such as in the case where the formation of blade, overhead 58 can be with Including the laminate that has been formed or as described in this article includes even CMC material but do not have metal core or open The laminate of mouth.
Once all required laminate one are stacked in another one and (in the case where if there is overhead) Be applied with overhead, then the manufacture of component can with any required process or it is any needed for process such as machine, coat and It is heat-treated and completes.In some embodiments, it would be desirable to, bigger Thermal protection is provided for component, especially for general The part for being exposed to high temperature provides bigger Thermal protection.In this case, when needed, the heat-insulating material of one or more layers Or thermal barrier coating can be applied to the periphery surface of component 30.In one embodiment, thermal barrier coating may include frangible Graded insulation layer (FGI), graded insulation layer (FGI) is well known in the art, such as United States Patent (USP) No.6,670,046 And No.6, as in 235,370, the two patents are incorporated herein by reference.In other embodiments, this thermal boundary Coating can be applied to the outer peripheral edge of each laminate 10,32 before laminate 10,32 is stacked.
Preceding paragraphs are elaborated for forming insertion in component 30 simultaneously by multiple laminates 10,32 forming members 30 One example process of formula internal cooling channel 22.However, it should be understood that the invention is not limited thereto.It can use and be used for Form component 30 described herein while no matter in which way any other suitable method of fenced cooling duct.Example Such as, metal support structure part does not need on the top surface of the laminate of newest placement of the tall ground vertically-arranged in stack.? In certain embodiments, the metal part being newly formed such as 64 or 64A can be shaped so that the metal portion being newly formed At least one section divided is flushed with the laminate 10,32 of the newest placement in current stack or lamination board group 66.At it In his some embodiments, the metal part being newly formed such as 64 or 64A can be shaped to so that at least partially will be by cloth It sets the laminate 10,32 of the newest placement in current stack or is laminated below the top surface of board group 66.It reiterates, uses During these methods and other methods by multiple stack laminate forming members can be used in this, and Elaborated in PCT application No.PCT/US2015/023017 for these methods from multiple stack laminate forming members with And other methods, the full content of the application are incorporated to by reference herein.
In some embodiments, metal support structure part 38 includes the form of relative symmetry, so that adjacent laminate Opening and the size of surrounding ontology be in contrast same or similar in whole part.In another embodiment, As being shown in FIG. 18, metal support structure part 38 can be formed by increasing material manufacturing, so that CMC laminate 10,32 Part and the part of metal support structure part 38 are stacked with, to make CMC laminate 10,32 (it is embedded with cooling duct 22) and gold Belong to supporting structure 38 to interlock in stack 25.In this way, the major part of metal support structure part 38 can with it is corresponding CMC laminate 10,32 be stacked with, thus such as vertically or engine radial direction is to CMC by metal support structure part 38 Laminate 10,32 is clamped.This structure may be under the conditions of specific load or in the thing for being individually laminated plate features There is provided in part individual laminate supporting member to avoid separation and leakage paths (internal cooling air leaks out or hot gas body drain Enter) it is useful.In the case where this limitation can be applied in rotating airfoils part, it will be carried from the centrifugation of each laminate Lotus is distributed to metal support structure part 38.In the case where blade, this method has better than following traditional spar shell concepts The advantages of: airfoil shell load is gathered in blade tips by the tradition spar shell concept, thus by by center of gravity towards leaf Piece taper is arranged and increases total blade loading.In one aspect of the invention, each lamination of the load transmission in stack It is carried out at plate, and therefore, load transmission can reduce centrifugal load.
Although various embodiments of the invention illustrated and described herein, it will be apparent that, only with Exemplary mode provides these embodiments.Herein, it can make a variety of changes, change in the case of without departing from the present invention Become and replaces.It is therefore intended that the present invention is limited only by the spirit and scope of the appended claims.

Claims (15)

1. a kind of component (30), comprising:
Multiple laminates (10,12), the multiple laminate one are stacked in another one to limit stack laminate structure (25), the stack laminate structure (25) has leading edge (18) and rear (20), in the multiple laminate (10,32) Each laminate includes ceramic-base complex material (11)；
Multiple internal cooling channels (22), the multiple internal cooling channel are limited at the stack laminate structure (25) Inside (21) in, each cooling duct in the cooling duct (22) is in the described of the stack laminate structure (25) It is longitudinally extended between leading edge (18) and the rear (20)；And
Metal support structure part (38), the metal support structure part (38) are arranged to extend through the laminate (10,32) In the first opening (28) and extend through the stack laminate structure (25).
2. gas turbine component according to claim 1, wherein the metal support structure part (38) includes to increase material The metal support structure part that mode manufactures.
3. component according to claim 1, wherein the cooling duct (22) includes in the transversal of polygonal shape (34) Face.
4. component according to claim 1, wherein the cooling duct (22) include depth from 1mm to 5mm and from The width of 1mm to 5mm.
5. component according to claim 1, wherein the metal support structure part (38) includes one or more radial directions Collection chamber (29), the collection chamber (29) extends through the stack laminate structure (25), and wherein, one Or more collection chamber (29) and the cooling duct (22) be in fluid communication so that being introduced in one or more gas collection Cooling fluid in room (29) is flowed into the cooling duct (22).
6. component according to claim 1, wherein the stack laminate structure (25) further includes outlet (26), institute Outlet (26) is stated to lead to the external environment of the component (30) and flow with the corresponding cooling duct in the cooling duct (22) Body connection.
7. component according to claim 1, wherein the component (30) includes the fixed part (70) of turbogenerator.
8. component according to claim 1, wherein the component (30) includes the rotating part (44) of turbogenerator.
9. one kind is used to form the process of component (30), the process includes:
It is limited by multiple first laminates (10) and the second laminate (32) around metal support structure part (38) are formed therein There are the stack laminate structure (25) of multiple internal cooling channels (22), first laminate (10) and second lamination Plate (32) respectively includes ceramic-base complex material (11), and first laminate (10) respectively further includes at least one positioned at it Cooling duct (22) in side, and the cooling duct (22) in the leading edge (18) and rear of first laminate (10) (20) it is longitudinally extended between.
10. process according to claim 9, wherein in corresponding laminate (10,32), one is stacked on shape in another one It is mentioned at carrying out fusing by the metal material (58,58A) to pantostrat before or after the component (30) and solidifying again For the metal support structure part (38).
11. process according to claim 9, further includes: pass through each first layer in first laminate (10) The cooling duct (22) is cut by laser out at least one surface (16,18) in pressing plate and in first laminate (10) Each of form the cooling duct (22) in the first laminate.
12. process according to claim 9, wherein by the way that the second laminate (32) is stacked on the first laminate (10) Above so that the top section of the cooling duct (22) of first laminate (10) is covered by second laminate (32) And by the effective temperature first laminate (10) to be linked to second laminate (32) to described first Laminate (10) and second laminate (32) are sintered and form the internal cooling channel (22).
13. process according to claim 9, wherein first laminate is provided with entrance (24) and outlet (26), institute It states entrance (24) to be located at the leading edge (18) or adjacent with the leading edge (18), the outlet (26) is located at the rear (20) adjacent at or with the rear (20), and the entrance (24) and the outlet (26) and the cooling duct (22) Fluid communication is flowed into cooling fluid in the entrance (24) and flows to institute by the cooling duct (22) State the outlet (26) of the first laminate (10).
14. process according to claim 9, further includes: offer extends through the stack laminate structure (25) One or more collection chambers (29), and wherein, one or more collection chamber (29) and the cooling duct (22) It is in fluid communication so that the cooling fluid being introduced in one or more collection chamber (29) travels into the cooling In channel (22).
15. process according to claim 9, wherein the process forms the fixation member (70) of gas-turbine unit Or rotary part (44).
CN201680084607.XA 2016-04-13 2016-04-13 Mixed component with internal cooling channel Pending CN109070552A (en)

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Application publication date: 20181221